Jezael Concepcion
Aerospace Engineer | Propulsion, Aerodynamics & Structural Analysis
Orlando Florida
ABOUT ME
Aerospace engineer with strong analytical and simulation-driven experience across propulsion systems, high-speed compressible flow, aerodynamics, CFD, and structural fracture mechanics. Demonstrated ability to translate theory into validated engineering insight through system-level design projects, numerical simulations, and parametric studies. Experienced with MATLAB, ANSYS Fluent, Abaqus, Python automation, and aerodynamic analysis tools. Seeking entry-level or associate aerospace engineering roles in propulsion, structures, aerodynamics, or systems engineering.
I’m currently seeking full-time opportunities in aerospace propulsion, systems engineering, or R&D, where I can contribute to mission-driven projects and continue growing as an engineer.
Long-term, I aim to contribute to technologies that enable deep space exploration, especially sustainable missions to Mars. Whether through propulsion, entry systems, or autonomous spacecraft, I want to help shape the future of interplanetary travel through grounded engineering and innovation.
Hypersonic Propulsion Test Facility Analysis (Mach 6)
Objective: Design and analytically evaluate a non-reacting hypersonic test facility capable of producing Mach 6 flow while maintaining a normal shock at the channel exit. Engineering Work: Derived nozzle area ratios to achieve Mach 6 flow...
Fracture Mechanics Analysis of Countersunk Fastener Holes
Objective: Quantify the effect of countersinking on Mode I stress intensity factors (SIFs) for edge cracks emanating from fastener holes—a geometry not addressed in standard fracture mechanics handbooks. Engineering Work: Built 3D Abaqus models of...
Viscous–Turbulent Wind Tunnel CFD Simulation
Objective Simulate and analyze viscous–turbulent flow through a contraction–test section–diffuser wind tunnel at multiple inlet velocities. Engineering Work Created 2D CFD models using air as an ideal gas with Sutherland viscosity Simulated inlet...
Comparative Aerodynamic Analysis of Wing Planforms
Objective: Compare aerodynamic performance of rectangular and tapered wings at different aspect ratios to inform low-speed aircraft design. Engineering Work: Generated NACA 2415 airfoil and four 3D wing configurations Aspect ratios: 6 and 12; taper...
Return-to-Launch-Site (RTLS) Reusable Rocket – Senior Design Capstone
Objective: Design, analyze, and validate a reusable launch vehicle concept capable of return-to-launch-site recovery, with emphasis on propulsion system selection, thrust margin optimization, and ascent/descent performance. Propulsion-Focused...